US2026085838A1PendingUtilityA1
Gas turbine engine
Est. expiryJun 10, 2044(~17.9 yrs left)· nominal 20-yr term from priority
F02C 7/228F02C 7/22F05D 2240/35F05D 2220/75F05D 2270/081F02C 9/40F23R 3/34
95
PatentIndex Score
0
Cited by
0
References
0
Claims
Abstract
A gas turbine engine includes a first and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater fuel flow rate than each of the second subset of fuel spray nozzles. A ratio of the first to the second subset of fuel spray nozzles is 1:2 to 1:5. A MTO nvPM emissions index ratio is:EImaxTO,SAFEImaxTO,FF.EImaxTO,SAF is the system loss corrected nvPM emissions index in mg/kg operating at around 100% available thrust if fuel provided to the fuel spray nozzles includes sustainable aviation fuel. EImaxTO,FF is the system loss corrected nvPM emissions index in mg/kg operating at around 100% available thrust if fuel provided to the plurality of fuel spray nozzles is fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1.
Claims
exact text as granted — not AI-modifiedWe claim:
1 . A gas turbine engine for an aircraft, comprising:
a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5; and wherein: a MTO nvPM emissions index ratio is defined as:
EI
max
TO
,
SAF
EI
max
TO
,
FF
where:
EI maxTO,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI maxTO,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine ( 10 ) when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel;
the MTO nvPM emissions index ratio of the gas turbine engine is less than 1; and
the gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles.
2 . The gas turbine engine of claim 1 , wherein the MTO nvPM emissions index ratio is less than or equal to 0.93, and preferably less than or equal to 0.86, and more preferably less than or equal to 0.79.
3 . The gas turbine engine of claim 1 , wherein the MTO nvPM emissions index ratio is greater than or equal to 0.15, and preferably greater than or equal to 0.3, and more preferably greater than or equal to 0.45.
4 . The gas turbine engine of claim 1 , wherein the MTO nvPM emissions index ratio is in the range of 0.516 to 0.776, and preferably in the range of 0.581 to 0.711, and more preferably in the range of 0.645 to 0.646.
5 . The gas turbine engine of claim 1 , wherein:
a climb nvPM emissions index ratio is defined as:
EI
climb
,
SAF
EI
climb
,
FF
where:
EI climb,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 85% available thrust for the given operating conditions, or for different given operating conditions, if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI climb,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 85% available thrust for the same given operating conditions at which EI climb,SAF is calculated and if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel;
and the climb nvPM emissions index ratio of the gas turbine engine is less than 1.
6 . The gas turbine engine of claim 5 , wherein the climb nvPM emissions index ratio is less than or equal to 0.9, and preferably less than or equal to 0.75, and more preferably less than or equal to 0.6.
7 . The gas turbine engine of claim 1 , wherein:
an approach nvPM emissions index ratio is defined as:
EI
approach
,
SAF
EI
approach
,
FF
where:
EI approach,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 30% available thrust for the given operating conditions, or for different given operating conditions, if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI approach,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 30% available thrust for the same given operating conditions at which EI approach,SAF is calculated and if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and
the approach nvPM emissions index ratio of the gas turbine engine is less than 1.
8 . The gas turbine engine of claim 7 , wherein the approach nvPM emissions index ratio is less than or equal to 0.8, and preferably less than or equal to 0.5, and more preferably less than or equal to 0.2.
9 . The gas turbine engine of claim 1 , wherein:
an idle nvPM emissions index ratio is defined as:
EI
idle
,
SAF
EI
idle
,
FF
where:
EI idle,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 7% available thrust for the given operating conditions, or for different given operating conditions, and if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI idle,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 7% available thrust for the same given operating conditions at which EI idle,SAF is calculated and if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and
the idle nvPM emissions index ratio of the gas turbine engine is less than 1.
10 . The gas turbine engine of claim 9 , wherein the idle nvPM emissions index ratio is less than or equal to 0.8, and preferably less than or equal to 0.5, and more preferably less than or equal to 0.2.
11 . The gas turbine engine of any of claim 9 , wherein the idle nvPM emissions index ratio is greater than or equal to 0.02, and preferably greater than or equal to 0.04, and more preferably greater than or equal to 0.06.
12 . The gas turbine engine of claim 9 , wherein the idle nvPM emissions index ratio is in the range of 0.0766 to 0.115, and preferably in the range of 0.0862 to 0.106, and more preferably in the range of 0.0958 to 0.0959
13 . The gas turbine engine of claim 1 , wherein the ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:3 to 1:4, or preferably in the range of 1:3.5 to 1:4.
14 . The gas turbine engine of claim 1 , wherein the combustor comprises one or more ignitors and wherein each of the first subset of fuel spray nozzles is located nearer a respective one or more of the ignitors than the second subset, and/or wherein one or more of the ignitors is arranged diametrically opposite another one or more of the ignitors.
15 . The gas turbine engine of claim 1 , wherein the fuel provided to the plurality of fuel spray nozzles comprises a % SAF in the range of 50% to 100%, preferably in the range 70% to 100%, and more preferably in the range 90% to 100%.
16 . A method of operating the gas turbine engine of claim 1 , the method comprising providing fuel comprising a sustainable aviation fuel to the plurality of fuel spray nozzles.
17 . A method of operating a gas turbine engine, the gas turbine engine comprising:
a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5; and wherein: a MTO nvPM emissions index ratio is defined as:
EI
max
TO
,
SAF
EI
max
TO
,
FF
where:
EI maxTO,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI maxTO,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and
the MTO nvPM emissions index ratio of the gas turbine engine is less than 1; and
the method comprises providing fuel comprising a sustainable aviation fuel to the plurality of fuel spray nozzles.
18 . The method of claim 17 , wherein:
a climb nvPM emissions index ratio is defined as:
EI
climb
,
SAF
EI
climb
,
FF
where:
EI climb,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 85% available thrust for the given operating conditions, or for different given operating conditions, if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI climb,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 85% available thrust for the same given operating conditions at which EI climb,SAF is determined and if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and
the climb nvPM emissions index ratio of the gas turbine engine is less than 1.
19 . The method of claim 17 , wherein:
an approach nvPM emissions index ratio is defined as:
EI
approach
,
SAF
EI
approach
,
FF
where:
EI approach,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 30% available thrust for the given operating conditions, or for different given operating conditions, if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI approach,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 30% available thrust for the same given operating conditions at which EI approach,SAF is determined and if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and
the approach nvPM emissions index ratio of the gas turbine engine is less than 1.
20 . The method of claim 17 , wherein:
an idle nvPM emissions index ratio is defined as:
EI
idle
,
SAF
EI
idle
,
FF
where:
EI idle,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 7% available thrust for the given operating conditions, or for different given operating conditions, and if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and
EI idle,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 7% available thrust for the same given operating conditions at which EI idle,SAF is determined and if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and
the idle nvPM emissions index ratio of the gas turbine engine is less than 1.Join the waitlist — get patent alerts
Track US2026085838A1 — get alerts on status changes and closely related new filings.
We store only your email — no account needed. See our privacy policy.